# ATEC 212 Solo

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212 Solo General information Type Ultralight aircraft National origin Czech Republic Manufacturer ATEC v.o.s. Status In production

The **ATEC 212 Solo** is a [Czech](/source/Czech_Republic) [ultralight aircraft](/source/Ultralight_aircraft), designed and produced by [ATEC v.o.s.](/source/ATEC_v.o.s.) of [Libice nad Cidlinou](/source/Libice_nad_Cidlinou). The aircraft is supplied as a complete ready-to-fly-aircraft.[1][2]

## Design and development

The aircraft was designed to comply with the [Fédération Aéronautique Internationale](/source/F%C3%A9d%C3%A9ration_A%C3%A9ronautique_Internationale) microlight rules. It features a cantilever [low-wing](/source/Low-wing), a single-seat, enclosed cockpit with a [bubble canopy](/source/Bubble_canopy), fixed [conventional landing gear](/source/Conventional_landing_gear) and a single engine in [tractor configuration](/source/Tractor_configuration).[1][2]

The 212 Solo is made from [carbon fibre](/source/Carbon_fibre) and was derived from the [ATEC 321 Faeta](/source/ATEC_321_Faeta) and [ATEC 122 Zephyr 2000](/source/ATEC_122_Zephyr_2000) designs. Its 7.48 m (24.5 ft) span wing employs an SM701 [airfoil](/source/Airfoil) and [slotted flaps](/source/Flap_(aircraft)). Standard engines available are the 64 hp (48 kW) [Rotax 582](/source/Rotax_582) [two-stroke](/source/Two-stroke) and the 80 hp (60 kW) [Rotax 912UL](/source/Rotax_912UL) [four-stroke](/source/Four-stroke) powerplant.[1][2]

## Specifications (212 Solo)

*Data from* Bayerl[1][2]

**General characteristics**

- **Crew:** one

- **Wingspan:** 7.48 m (24 ft 6 in)

- **Wing area:** 7.27 m2 (78.3 sq ft)

- **Empty weight:** 200 kg (441 lb)

- **Gross weight:** 315 kg (694 lb)

- **Fuel capacity:** 50 litres (11 imp gal; 13 US gal)

- **Powerplant:** 1 × [Rotax 582](/source/Rotax_582) twin cylinder, liquid-cooled, [two stroke](/source/Two_stroke), 48 kW (64 hp)

- **Propellers:** 3-bladed composite

**Performance**

- **Maximum speed:** 250 km/h (160 mph, 130 kn)

- **Cruise speed:** 220 km/h (140 mph, 120 kn)

- **Stall speed:** 65 km/h (40 mph, 35 kn)

- **Rate of climb:** 7 m/s (1,400 ft/min)

- **Wing loading:** 43.32 kg/m2 (8.87 lb/sq ft)

## References

1. ^ [***a***](#cite_ref-WDLA11_1-0) [***b***](#cite_ref-WDLA11_1-1) [***c***](#cite_ref-WDLA11_1-2) [***d***](#cite_ref-WDLA11_1-3) Bayerl, Robby; Martin Berkemeier; et al: *World Directory of Leisure Aviation 2011-12*, page 28. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X

1. ^ [***a***](#cite_ref-WDLA15_2-0) [***b***](#cite_ref-WDLA15_2-1) [***c***](#cite_ref-WDLA15_2-2) [***d***](#cite_ref-WDLA15_2-3) Tacke, Willi; Marino Boric; et al: *World Directory of Light Aviation 2015-16*, page 29. Flying Pages Europe SARL, 2015. [ISSN](/source/ISSN_(identifier)) [1368-485X](https://search.worldcat.org/issn/1368-485X)

## External links

- [Official website](https://www.atecaircraft.eu/en/planes/atec-212-solo)

v t e ATEC aircraft Ultralight aircraft 122 Zephyr 2000 212 Solo 321 Faeta

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Adapted from the Wikipedia article [ATEC 212 Solo](https://en.wikipedia.org/wiki/ATEC_212_Solo) by Wikipedia contributors ([contributor history](https://en.wikipedia.org/wiki/ATEC_212_Solo?action=history)). Available under [Creative Commons Attribution-ShareAlike 4.0 International](https://creativecommons.org/licenses/by-sa/4.0/). Changes may have been made.